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A Rapid Design Method for Inspection Fixtures of Aircraft Sheet Metal Parts

A technology of aircraft sheet metal and design method, applied in the direction of calculation, instrument, geometric CAD, etc., can solve the problems of wasting design time, heavy design workload, repeated design, etc.

Active Publication Date: 2022-05-06
JIANGXI HONGDU AVIATION IND GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since there is no uniform, standard, and fast design method, the design workload of the template is huge, and there is a problem of repeated design and change of one type of part, which wastes a lot of design time and seriously affects the design cycle.
[0004] It is very necessary and meaningful to design a rapid design method for aircraft sheet metal parts inspection tools to solve the problems of repeated template design and long design cycle

Method used

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  • A Rapid Design Method for Inspection Fixtures of Aircraft Sheet Metal Parts
  • A Rapid Design Method for Inspection Fixtures of Aircraft Sheet Metal Parts
  • A Rapid Design Method for Inspection Fixtures of Aircraft Sheet Metal Parts

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Embodiment Construction

[0032] The following will combine Figure 1 to Figure 3 , clearly and completely describe the technical solutions in the embodiments of the invention.

[0033] by figure 1 The part model shown as an example, combined with figure 2 and image 3 , to illustrate the specific implementation process of the template rapid design.

[0034] figure 1 Shown is a rib plate part of a certain model, including structural features such as 1 web surface 1, 2 flange surfaces 2, 6 sunken surfaces 3, 1 flange relief hole 4, and 1 through hole 5. Among them, the web surface 1 is a plane, and the two flange surfaces 2 are both hyperbolic surfaces.

[0035] The first step is to establish the model design reference plane:

[0036] Such as figure 1 As shown in the 3D model of the part, the web surface 1 of the part is selected as the reference plane to establish the template design plane.

[0037] The second step is to simplify the product 3D model:

[0038] Such as figure 1 As shown, the ...

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Abstract

The invention provides a rapid design method for inspection tools of aircraft sheet metal parts. The method uses the secondary development plug-in of the three-dimensional model of the aircraft part product, and establishes the reference plane of the model design, simplifies the three-dimensional model of the product, generates the contour line of the model, and generates the slope of the model. Corner, select the mark to be added, add the position of the process hole, add the internal scribe line of the template, expand the calculation, add the template supplement, import the template process drawing template and other steps, quickly and standardize the design of the required template. The rapid design method proposed by the invention can be directly used in the standardized design of the template, which facilitates the operation of the template designer and shortens the design cycle of different models and different varieties of templates.

Description

technical field [0001] The invention belongs to the field of mechanical manufacturing design, in particular to a rapid design method for inspection tools of aircraft sheet metal parts. Background technique [0002] In the structural parts of modern aircraft, there are still a large number of sheet metal formed parts, usually of different thicknesses. Due to the thin thickness of sheet metal parts, most complex sheet metal parts are deformed after being formed by machine tools, and a lot of manual work is still required after forming. A fast and practical checking tool is required in the manual calibration process and the final delivery process of the parts. [0003] As a kind of aviation process equipment, the template has always been used as a check tool in the manufacturing process of aircraft sheet metal parts. Usually, a sheet metal part requires multiple samples of different varieties to be used together in the calibration and delivery process. Since there is no unif...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15G06F30/17G06T17/00
CPCG06F30/15G06F30/17G06T17/00
Inventor 李仁花宋利康陈志敏张文俊程世明刘洋洋曹唐珍雷玉如熊国翠王莉王琳朱江成
Owner JIANGXI HONGDU AVIATION IND GRP